Analysis of a hydrocarbon scramjet with augmented preburningThis paper presents the results of a feasibility study of a hydrocarbon scramjet design utilizing an augmented preburner upstream of the main fuel injector locations. The combustor design evaluated here is for a small hypersonic research vehicle. It consists of a preburner into which a small amount of fuel is burned with on-board liquid oxygen and injected into the main airflow, upstream of the main fuel injector locations, thus ensuring that combustion is present and uninterrupted. Two degrees of analysis are presented including a one-dimensional cycle analysis and a complete computational fluid dynamic analysis with finite-rate chemistry and a two-equation turbulence model. Comparison of these analyses show good agreement when the CFD-predicted fuel consumption schedule is used in the cycle analysis.
Document ID
19920066360
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Molvik, Gregory A. (NASA Ames Research Center Moffett Field, CA, United States)
Bowles, Jeffrey V. (NASA Ames Research Center Moffett Field, CA, United States)
Huynh, Loc C. (NASA Ames Research Center Moffett Field, CA, United States)